2.3 Intelligent Engine Systems 2.3.3.2 Advanced Film Cooling Techniques

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2.3 Intelligent Engine Systems2.3.3.2 Advanced
Film Cooling Techniques
Dunn (Ohio State University)

• Science Technology Objective(s)
• Obtain a detailed film cooling data base under
  laboratory controlled conditions for a
  state-of-the-art turbine stage. All of the
  relevant design parameters must be duplicated for
  this measurement program.

• Photograph of Film Cooled Vane Blade

• Collaborations
• Government - NASA Glenn Research Center
• Industry - Honeywell, General Electric Aircraft
  Engines, Pratt/Whitney
• URETI - OSU Georgia Tech.
• Synergism - Allied Signal GEAE programs

• Proposed Approach
• Permission obtained to use TFE 1042 turbine
  stage.
• Complete advanced instrumentation development.
• Complete rig assembly and verification.
• Perform measurement program, data reduction and
  analysis.

• Milestones/Accomplishments
• Complete development of Kapton gauge
  instrumentation
• Install Kapton gauges on vanes blades
• Complete rig assembly cooling system
  verification
• Determine film cooling effectiveness for
• Engine values of Tc/Tg, Tc/Tw, Tw/Tg
• Engine design corrected speed Flow Function
• Measurements to include heat transfer, gas
  temperatures, and relevant pressures
• Complete analysis of experimental results
• Initiate development of film cooling macro model

• NASA Air Force Relevance/Impact
• Film cooling data set for full-stage rotating
  turbine does not presently exist.
• Will have significant impact on development of
  film cooling modeling and CFD code development.

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2.3.3.2 Proposed Approach

• The ability to design and control efficient
  film-cooling schemes is essential for development
  of advanced engines. This will ensure safe and
  reliable operation with reduced operating costs.
  A major limitation is the the absence of
  experimental results for flow conditions
  associated with realistic turbine operating
  conditions, which would permit design of
  improved, and controllable, film cooling systems.
• The Proposed approach is to utilize the existing
  Honeywell TFE 1042 fully cooled HPT turbine stage
  and the associated rig hardware to obtain the
  required experimental results.
• Research effort will be performed in two phases
  (1) with cooling system as designed by
  manufacturer and (2) miniature control/feedback
  to selectively control cooling flow.